[go: up one dir, main page]

US10240481B2 - Angled cut to direct radiative heat load - Google Patents

Angled cut to direct radiative heat load Download PDF

Info

Publication number
US10240481B2
US10240481B2 US14/758,267 US201314758267A US10240481B2 US 10240481 B2 US10240481 B2 US 10240481B2 US 201314758267 A US201314758267 A US 201314758267A US 10240481 B2 US10240481 B2 US 10240481B2
Authority
US
United States
Prior art keywords
fairing
turbine exhaust
exhaust case
heat shield
frame
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active, expires
Application number
US14/758,267
Other languages
English (en)
Other versions
US20150337683A1 (en
Inventor
Jonathan Ariel Scott
Conway Chuong
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Priority to US14/758,267 priority Critical patent/US10240481B2/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Chuong, Conway, SCOTT, JONATHAN ARIEL
Publication of US20150337683A1 publication Critical patent/US20150337683A1/en
Application granted granted Critical
Publication of US10240481B2 publication Critical patent/US10240481B2/en
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS. Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RTX CORPORATION reassignment RTX CORPORATION CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: RAYTHEON TECHNOLOGIES CORPORATION
Active legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids

Definitions

  • the present disclosure relates generally to gas turbine engines, and more particularly to heat management in a turbine exhaust case of a gas turbine engine.
  • a turbine exhaust case is a structural frame that supports engine bearing loads while providing a gas path at or near the aft end of a gas turbine engine.
  • Some aeroengines utilize a turbine exhaust case to help mount the gas turbine engine to an aircraft airframe.
  • a turbine exhaust case is more commonly used to couple gas turbine engines to a power turbine that powers an electrical generator.
  • Industrial turbine exhaust cases can, for instance, be situated between a low pressure engine turbine and a generator power turbine.
  • a turbine exhaust case must bear shaft loads from interior bearings, and must be capable of sustained operation at high temperatures.
  • Turbine exhaust cases serve two primary purposes: airflow channeling and structural support.
  • Turbine exhaust cases typically comprise structures with inner and outer rings connected by radial struts.
  • the struts and rings often define a core flow path from fore to aft, while simultaneously mechanically supporting shaft bearings situated axially inward of the inner ring.
  • the components of a turbine exhaust case are exposed to very high temperatures along the core flow path.
  • Various approaches and architectures have been employed to handle these high temperatures.
  • Some turbine exhaust case frames utilize high-temperature, high-stress capable materials to both define the core flow path and bear mechanical loads.
  • Other frame architectures separate these two functions, pairing a structural frame for mechanical loads with a high-temperature capable fairing to define the core flow path.
  • Superalloys capable of operating in the high temperatures of the core flow path are commonly expensive and difficult to machine.
  • the present disclosure is directed toward a fairing comprising an inner platform, an outer platform, a plurality of vane bodies, and a flange.
  • the inner and outer platforms define radially inner and outer boundaries of an airflow path.
  • the vane bodies extend radially from the inner platform to the outer ring.
  • the flange extends radially outward from the outer platform, and is defined by a frustoconical surface extending radially inward and axially aft from a substantially radial upstream surface.
  • FIG. 1 is a simplified partial cross-sectional view of an embodiment of a gas turbine engine.
  • FIG. 2 is a cross-sectional view of a turbine exhaust case of the gas turbine engine of FIG. 1 .
  • FIG. 1 is a simplified partial cross-sectional view of gas turbine engine 10 , comprising inlet 12 , compressor 14 (with low pressure compressor 16 and high pressure compressor 18 ), combustor 20 , engine turbine 22 (with high pressure turbine 24 and low pressure turbine 26 ), turbine exhaust case 28 , power turbine 30 , low pressure shaft 32 , high pressure shaft 34 , and power shaft 36 .
  • Gas turbine engine 10 can, for instance, be an industrial power turbine.
  • Low pressure shaft 32 , high pressure shaft 34 , and power shaft 36 are situated along rotational axis A.
  • low pressure shaft 32 and high pressure shaft 34 are arranged concentrically, while power shaft 36 is disposed axially aft of low pressure shaft 32 and high pressure shaft 34 .
  • Low pressure shaft 32 defines a low pressure spool including low pressure compressor 16 and low pressure turbine 26 .
  • High pressure shaft 34 analogously defines a high pressure spool including high pressure compressor 18 and high pressure compressor 24 .
  • airflow F is received at inlet 12 , then pressurized by low pressure compressor 16 and high pressure compressor 18 .
  • Fuel is injected at combustor 20 , where the resulting fuel-air mixture is ignited.
  • Expanding combustion gasses rotate high pressure turbine 24 and low pressure turbine 26 , thereby driving high and low pressure compressors 18 and 16 through high pressure shaft 34 and low pressure shaft 32 , respectively.
  • compressor 14 and engine turbine 22 are depicted as two-spool components with high and low sections on separate shafts, single spool or 3+ spool embodiments of compressor 14 and engine turbine 22 are also possible.
  • Turbine exhaust case 28 carries airflow from low pressure turbine 26 to power turbine 30 , where this airflow drives power shaft 36 .
  • Power shaft 36 can, for instance, drive an electrical generator, pump, mechanical gearbox, or other accessory (not shown).
  • turbine exhaust case 28 can support one or more shaft loads.
  • Turbine exhaust case 28 can, for instance, support low pressure shaft 32 via bearing compartments (not shown) disposed to communicate load from low pressure shaft 32 to a structural frame of turbine exhaust case 28 .
  • FIG. 2 is a cross-sectional view of an embodiment of turbine exhaust case 28 , illustrating frame 102 (with frame outer ring 104 , frame inner ring 106 , frame struts 108 , low pressure turbine connection 110 , and power turbine connection 112 ), bearing support 114 , fasteners 116 a and 116 b , fairing 118 (with fairing outer platform 120 , fairing inner platform 122 , and fairing vanes 124 ), forward stiffening flange 126 , aft stiffening flange 128 , strut heat shield 132 , outer heat shield 134 , and inner heat shield 136 .
  • turbine exhaust case 28 defines at least a portion of an airflow path for core flow F, and carries load radially from bearing support 114 (which in turn connects to bearing components, not shown). These two functions are performed by separate components: frame 102 carries bearing loads, while fairing 118 at least partially defines the flow path of core flow F.
  • Frame 102 is a relatively thick, rigid support structure formed, for example, of cast steel.
  • Outer ring 104 of frame 102 serves as an attachment point for upstream and downstream components at low pressure turbine connection 110 and power turbine connection 112 , respectively.
  • Low pressure turbine connection 110 and power turbine connection 112 can, for instance, include fastener holes for attachment to adjacent low pressure turbine 26 and power turbine 30 , respectively.
  • Frame inner ring 106 is mechanically connected to bearing support 114 via fasteners 116 a , which can for instance be bolts, screws, pins or rivets.
  • Frame inner ring 106 communicates bearing load radially from bearing support 114 to frame outer ring 104 via frame struts 108 , which extend at angular intervals between frame inner ring 106 and frame outer ring 104 .
  • frame struts 108 extend at angular intervals between frame inner ring 106 and frame outer ring 104 .
  • turbine exhaust case 28 can include any desired number of struts 108 .
  • Fairing 118 is a high-temperature capable aerodynamic structure at least partially defining the boundaries of core flow F through turbine exhaust case 28 .
  • Fairing outer platform 120 generally defines an outer flowpath diameter
  • fairing inner platform 122 generally defines an inner flowpath diameter.
  • Fairing vanes 124 surround frame struts 108 , and form a plurality of aerodynamic vane bodies.
  • Fairing 118 can, for instance, be formed of a superalloy material such as Inconel or other nickel-based superalloy. Fairing 118 is generally rated for higher temperatures than frame 102 , and can be affixed to frame 102 via fasteners 116 b .
  • fairing 118 is affixed to frame inner ring 106 at the forward inner diameter of fairing 118 , although alternative embodiments of turbine exhaust case 28 can secure fairing 118 by other means and/or in other locations.
  • Forward and aft stiffening flanges 126 and 128 can extend radially outward from the entire circumference of fairing outer platform 120 to provide increased structural rigidity to fairing 118 .
  • Turbine exhaust case 28 includes a plurality of heat shields to protect frame 102 from radiative and convective heating.
  • Strut heat shield 132 is situated between fairing vanes 124 and frame struts 108 .
  • Outer heat shield 134 can be situated between fairing outer platform 120 and frame outer ring 104 .
  • Inner heat shield 136 can be is situated radially inward of a forward portion of fairing inner platform 122 .
  • all three heat shields 132 , 134 , and 136 can be formed of Inconel or a similar nickel-based superalloy.
  • Strut heat shield 132 , outer heat shield 134 , and inner heat shield 136 act as barriers to heat from fairing 118 , which can become very hot during operation of gas turbine 10 .
  • Heat shields 132 , 134 , and 136 thus help to protect frame 102 , which can be rated to lower temperatures than fairing 118 , from exposure to excessive heat.
  • Angled cut S defines angled cut surface S O , a frustoconical outer surface extending radially inward and axially aft from substantially radial forward surface S F of forward stiffening flange 126 .
  • angled cut surface S O is a chamfer that extends axially to substantially radial aft flange surface S A .
  • angled cut surface S O can extend to fairing outer platform 120 .
  • Angled cut surface S O radiates primarily in a direction normal to cut surface S O , i.e. towards outer heat shield 134 , thereby reducing radiative heating of frame 102 . Angled cut S thus enables cooler operation of frame 102 by minimizing the radiative heat load on frame 102 from stiffening flange 126 .
  • a fairing comprising an inner platform, an outer platform, a plurality of vane bodies, and a flange.
  • the inner and outer platforms define radially inner and outer boundaries, respectively, of an airflow path.
  • Each of the plurality of vane bodies extends radially from the inner platform to the outer platform.
  • the flange extends radially outward from the inner platform, and is defined by a frustoconical surface extending radially inward and axially aft from a substantially radial upstream surface.
  • the fairing of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations, and/or additional components:
  • the fairing is formed of a nickel-based superalloy.
  • the fairing further comprises a second flange extending radially outward from the outer platform at a location axially aft of the first flange.
  • frustoconical surface extends radially inward and axially aft to a substantially radial aft surface.
  • a turbine exhaust case comprising a frame and a fairing.
  • the frame has inner and outer rings connected by a plurality of radial struts.
  • the fairing is situated between the inner and outer rings to define an airflow path, and comprises an inner platform, an outer platform, a plurality of vane bodies, and a stiffening flange.
  • the inner platform is situated radially inward of the inner ring.
  • the outer platform is situated radially inward of the outer ring.
  • Each of the plurality of vane bodies extends from the inner platform to the outer platform, and surrounds a radial strut.
  • the stiffening flange extends radially outward from the outer platform, and is defined by a frustoconical surface extending radially inward and axially aft from a substantially radial upstream surface.
  • the turbine exhaust case of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations, and/or additional components:
  • a radiative heat shield disposed between the fairing and the frame, such that the radiative heat shield and the fairing together define a secondary airflow path that the radially outermost surface of the stiffening flange directs away from the frame.
  • the radiative heat shield comprises an outer heat shield and a strut heat shield, and wherein the secondary airflow path flows between the outer heat shield and the outer platform of the heat shield.
  • fairing and the radiative heat shield are formed of a nickel-based superalloy
  • the frame is formed of cast steel.
  • the airflow path carries core airflow from a low pressure turbine immediately forward of the turbine exhaust case to power turbine immediately aft of the turbine exhaust case.
  • a method of protecting a turbine exhaust case frame from overheating comprises defining a core airflow path through the turbine exhaust case frame with a fairing having at least one radially-extending stiffening flange, situating a radiative heat shield between the fairing and the turbine exhaust case such that the radiative heat shield and the fairing together define a secondary airflow path, and directing hot air from the secondary airflow path away from the turbine exhaust case frame via a frustoconical surface of the stiffening flange extending radially inward and axially aft from a radial upstream surface of the stiffening flange.
  • the method of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations, and/or additional components:
  • the radiative heat shield and the fairing are formed of a nickel-based superalloy.
  • turbine exhaust case frame is formed of steel.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US14/758,267 2012-12-29 2013-12-19 Angled cut to direct radiative heat load Active 2036-03-25 US10240481B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US14/758,267 US10240481B2 (en) 2012-12-29 2013-12-19 Angled cut to direct radiative heat load

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US201261747256P 2012-12-29 2012-12-29
US14/758,267 US10240481B2 (en) 2012-12-29 2013-12-19 Angled cut to direct radiative heat load
PCT/US2013/076394 WO2014105604A1 (fr) 2012-12-29 2013-12-19 Découpe oblique permettant de diriger une charge de chaleur par rayonnement

Publications (2)

Publication Number Publication Date
US20150337683A1 US20150337683A1 (en) 2015-11-26
US10240481B2 true US10240481B2 (en) 2019-03-26

Family

ID=51021968

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/758,267 Active 2036-03-25 US10240481B2 (en) 2012-12-29 2013-12-19 Angled cut to direct radiative heat load

Country Status (2)

Country Link
US (1) US10240481B2 (fr)
WO (1) WO2014105604A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3110201B1 (fr) * 2020-05-15 2022-04-08 Safran Aircraft Engines Carter d’échappement de turbomachine

Citations (159)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2214108A (en) 1938-11-05 1940-09-10 Gen Motors Corp Manufacture of tubing
US3576328A (en) 1968-03-22 1971-04-27 Robert W Vose High pressure seals
US3802046A (en) 1972-01-27 1974-04-09 Chromalloy American Corp Method of making or reconditioning a turbine-nozzle or the like assembly
US3970319A (en) 1972-11-17 1976-07-20 General Motors Corporation Seal structure
US4009569A (en) 1975-07-21 1977-03-01 United Technologies Corporation Diffuser-burner casing for a gas turbine engine
US4044555A (en) 1958-09-30 1977-08-30 Hayes International Corporation Rear section of jet power plant installations
US4079587A (en) * 1975-12-10 1978-03-21 Stal-Laval Turbin Ab Multi-stage turbine with interstage spacer-manifold for coolant flow
US4088422A (en) 1976-10-01 1978-05-09 General Electric Company Flexible interstage turbine spacer
US4114248A (en) 1974-12-23 1978-09-19 United Technologies Corporation Method of making resiliently coated metallic finger seals
US4190397A (en) * 1977-11-23 1980-02-26 General Electric Company Windage shield
US4305697A (en) 1980-03-19 1981-12-15 General Electric Company Method and replacement member for repairing a gas turbine engine vane assembly
US4321007A (en) 1979-12-21 1982-03-23 United Technologies Corporation Outer case cooling for a turbine intermediate case
US4369016A (en) 1979-12-21 1983-01-18 United Technologies Corporation Turbine intermediate case
US4478551A (en) 1981-12-08 1984-10-23 United Technologies Corporation Turbine exhaust case design
US4645217A (en) 1985-11-29 1987-02-24 United Technologies Corporation Finger seal assembly
US4678113A (en) 1985-02-20 1987-07-07 Rolls-Royce Plc Brush seals
US4738453A (en) 1987-08-17 1988-04-19 Ide Russell D Hydrodynamic face seal with lift pads
US4756536A (en) 1986-12-06 1988-07-12 Rolls-Royce Plc Brush seal
US4793770A (en) 1987-08-06 1988-12-27 General Electric Company Gas turbine engine frame assembly
US4920742A (en) 1988-05-31 1990-05-01 General Electric Company Heat shield for gas turbine engine frame
US4979872A (en) * 1989-06-22 1990-12-25 United Technologies Corporation Bearing compartment support
US4987736A (en) 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
US4989406A (en) 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
US4993918A (en) 1989-05-19 1991-02-19 United Technologies Corporation Replaceable fairing for a turbine exhaust case
US5031922A (en) 1989-12-21 1991-07-16 Allied-Signal Inc. Bidirectional finger seal
US5042823A (en) 1989-12-21 1991-08-27 Allied-Signal Inc. Laminated finger seal
US5071138A (en) 1989-12-21 1991-12-10 Allied-Signal Inc. Laminated finger seal
US5076049A (en) 1990-04-02 1991-12-31 General Electric Company Pretensioned frame
US5100158A (en) 1990-08-16 1992-03-31 Eg&G Sealol, Inc. Compliant finer seal
US5108116A (en) 1991-05-31 1992-04-28 Allied-Signal Inc. Laminated finger seal with logarithmic curvature
US5115642A (en) * 1991-01-07 1992-05-26 United Technologies Corporation Gas turbine engine case with intergral shroud support ribs
US5169159A (en) 1991-09-30 1992-12-08 General Electric Company Effective sealing device for engine flowpath
US5174584A (en) 1991-07-15 1992-12-29 General Electric Company Fluid bearing face seal for gas turbine engines
US5188507A (en) 1991-11-27 1993-02-23 General Electric Company Low-pressure turbine shroud
US5211541A (en) 1991-12-23 1993-05-18 General Electric Company Turbine support assembly including turbine heat shield and bolt retainer assembly
US5236302A (en) 1991-10-30 1993-08-17 General Electric Company Turbine disk interstage seal system
US5246295A (en) 1991-10-30 1993-09-21 Ide Russell D Non-contacting mechanical face seal of the gap-type
US5265807A (en) 1992-06-01 1993-11-30 Rohr, Inc. Aerodynamic stiffening ring for an aircraft turbine engine mixer
US5269057A (en) 1991-12-24 1993-12-14 Freedom Forge Corporation Method of making replacement airfoil components
US5273397A (en) 1993-01-13 1993-12-28 General Electric Company Turbine casing and radiation shield
US5272869A (en) 1992-12-10 1993-12-28 General Electric Company Turbine frame
US5292227A (en) 1992-12-10 1994-03-08 General Electric Company Turbine frame
US5312227A (en) 1991-12-18 1994-05-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbine casing delimiting an annular gas flow stream divided by radial arms
US5338154A (en) 1993-03-17 1994-08-16 General Electric Company Turbine disk interstage seal axial retaining ring
US5357744A (en) 1992-06-09 1994-10-25 General Electric Company Segmented turbine flowpath assembly
US5370402A (en) 1993-05-07 1994-12-06 Eg&G Sealol, Inc. Pressure balanced compliant seal device
US5401036A (en) 1993-03-22 1995-03-28 Eg & G Sealol, Inc. Brush seal device having a recessed back plate
US5438756A (en) 1993-12-17 1995-08-08 General Electric Company Method for assembling a turbine frame assembly
US5474305A (en) 1990-09-18 1995-12-12 Cross Manufacturing Company (1938) Limited Sealing device
US5483792A (en) 1993-05-05 1996-01-16 General Electric Company Turbine frame stiffening rails
US5558341A (en) 1995-01-11 1996-09-24 Stein Seal Company Seal for sealing an incompressible fluid between a relatively stationary seal and a movable member
US5597286A (en) 1995-12-21 1997-01-28 General Electric Company Turbine frame static seal
US5605438A (en) 1995-12-29 1997-02-25 General Electric Co. Casing distortion control for rotating machinery
US5609467A (en) 1995-09-28 1997-03-11 Cooper Cameron Corporation Floating interturbine duct assembly for high temperature power turbine
US5632493A (en) 1995-05-04 1997-05-27 Eg&G Sealol, Inc. Compliant pressure balanced seal apparatus
US5634767A (en) 1996-03-29 1997-06-03 General Electric Company Turbine frame having spindle mounted liner
US5691279A (en) 1993-06-22 1997-11-25 The United States Of America As Represented By The Secretary Of The Army C-axis oriented high temperature superconductors deposited onto new compositions of garnet
US5755445A (en) 1996-08-23 1998-05-26 Alliedsignal Inc. Noncontacting finger seal with hydrodynamic foot portion
US5851105A (en) 1995-06-28 1998-12-22 General Electric Company Tapered strut frame
US5911400A (en) 1995-09-27 1999-06-15 Hydraulik-Ring Antriebs-Und Steuerungstechnik Gmbh Solenoid valve and method for its manufacture
US6163959A (en) 1998-04-09 2000-12-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Method of reducing the gap between a liner and a turbine distributor of a turbojet engine
US6179560B1 (en) 1998-12-16 2001-01-30 United Technologies Corporation Turbomachinery module with improved maintainability
US6196550B1 (en) 1999-02-11 2001-03-06 Alliedsignal Inc. Pressure balanced finger seal
US6227800B1 (en) 1998-11-24 2001-05-08 General Electric Company Bay cooled turbine casing
US6337751B1 (en) 1997-08-26 2002-01-08 Canon Kabushiki Kaisha Sheet feeding apparatus and image processing apparatus
US6343912B1 (en) 1999-12-07 2002-02-05 General Electric Company Gas turbine or jet engine stator vane frame
US6358001B1 (en) 2000-04-29 2002-03-19 General Electric Company Turbine frame assembly
US6364316B1 (en) 1999-02-11 2002-04-02 Honeywell International Inc. Dual pressure balanced noncontacting finger seal
US6439841B1 (en) 2000-04-29 2002-08-27 General Electric Company Turbine frame assembly
US6511284B2 (en) 2001-06-01 2003-01-28 General Electric Company Methods and apparatus for minimizing gas turbine engine thermal stress
US20030025274A1 (en) 2001-08-02 2003-02-06 Honeywell International, Inc. Laminated finger seal with stress reduction
US20030042682A1 (en) 2001-08-29 2003-03-06 Eagle Industry Co., Ltd. Brush seal device
WO2003020469A1 (fr) 2001-08-29 2003-03-13 Volvo Aero Corporation Procede de fabrication d'element de stator ou de rotor
US20030062684A1 (en) 2001-09-28 2003-04-03 Eagle Industry Co., Ltd. Brush seal
US20030062685A1 (en) 2001-09-28 2003-04-03 Eagle Industry Co., Ltd Brush seal and brush seal device
US6578363B2 (en) 2001-03-05 2003-06-17 Mitsubishi Heavy Industries, Ltd. Air-cooled gas turbine exhaust casing
US6601853B2 (en) 2001-06-29 2003-08-05 Eagle Industry Co., Ltd. Brush seal device
US6612807B2 (en) 2001-11-15 2003-09-02 General Electric Company Frame hub heating system
US6619030B1 (en) 2002-03-01 2003-09-16 General Electric Company Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors
US6638013B2 (en) 2002-02-25 2003-10-28 Honeywell International Inc. Thermally isolated housing in gas turbine engine
US6652229B2 (en) 2002-02-27 2003-11-25 General Electric Company Leaf seal support for inner band of a turbine nozzle in a gas turbine engine
US6672833B2 (en) 2001-12-18 2004-01-06 General Electric Company Gas turbine engine frame flowpath liner support
US6719524B2 (en) 2002-02-25 2004-04-13 Honeywell International Inc. Method of forming a thermally isolated gas turbine engine housing
US6736401B2 (en) 2001-12-19 2004-05-18 Honeywell International, Inc. Laminated finger seal with ceramic composition
US6792758B2 (en) 2002-11-07 2004-09-21 Siemens Westinghouse Power Corporation Variable exhaust struts shields
US6796765B2 (en) 2001-12-27 2004-09-28 General Electric Company Methods and apparatus for assembling gas turbine engine struts
US6811154B2 (en) 2003-02-08 2004-11-02 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Noncontacting finger seal
US20050046113A1 (en) 2002-05-23 2005-03-03 Eagle Industry Co., Ltd. Sheet brush seal
US6969826B2 (en) 2004-04-08 2005-11-29 General Electric Company Welding process
US6983608B2 (en) 2003-12-22 2006-01-10 General Electric Company Methods and apparatus for assembling gas turbine engines
US20060010852A1 (en) 2004-07-16 2006-01-19 Pratt & Whitney Canada Corp. Turbine exhaust case and method of making
US7055305B2 (en) 2002-02-09 2006-06-06 Alstom Technology Ltd Exhaust gas housing of a thermal engine
US7094026B2 (en) 2004-04-29 2006-08-22 General Electric Company System for sealing an inner retainer segment and support ring in a gas turbine and methods therefor
US7200933B2 (en) 2002-08-14 2007-04-10 Volvo Aero Corporation Method for manufacturing a stator component
US7229249B2 (en) 2004-08-27 2007-06-12 Pratt & Whitney Canada Corp. Lightweight annular interturbine duct
US7238008B2 (en) 2004-05-28 2007-07-03 General Electric Company Turbine blade retainer seal
US7249463B2 (en) * 2004-09-15 2007-07-31 General Electric Company Aerodynamic fastener shield for turbomachine
US7367567B2 (en) 2005-03-02 2008-05-06 United Technologies Corporation Low leakage finger seal
US7371044B2 (en) 2005-10-06 2008-05-13 Siemens Power Generation, Inc. Seal plate for turbine rotor assembly between turbine blade and turbine vane
US7389583B2 (en) 2003-03-21 2008-06-24 Volvo Aero Corporation Method of manufacturing a stator component
US20080216300A1 (en) 2007-03-06 2008-09-11 United Technologies Corporation Splitter fairing repair
US20090053046A1 (en) * 2007-08-23 2009-02-26 General Electric Company Method, system and apparatus for turbine diffuser sealing
US20090155069A1 (en) 2007-12-12 2009-06-18 Eric Durocher Axial loading element for turbine vane
US7614150B2 (en) 2002-08-14 2009-11-10 Volvo Aero Corporation Method for manufacturing a stator or rotor component
US7631879B2 (en) 2006-06-21 2009-12-15 General Electric Company “L” butt gap seal between segments in seal assemblies
WO2009157817A1 (fr) 2008-06-26 2009-12-30 Volvo Aero Corporation Ensemble aube, procédé de fabrication associé, et turbomachine équipée de cet ensemble aube
WO2010002295A1 (fr) 2008-07-04 2010-01-07 Volvo Aero Corporation Procédé de soudage
US7673461B2 (en) 2005-09-29 2010-03-09 Snecma Structural turbine engine casing
US20100061846A1 (en) 2008-09-05 2010-03-11 United Technologies Corporation Repaired turbine exhaust strut heat shield vanes and repair methods
US7677047B2 (en) 2006-03-29 2010-03-16 United Technologies Corporation Inverted stiffened shell panel torque transmission for loaded struts and mid-turbine frames
US20100132377A1 (en) 2008-11-28 2010-06-03 Pratt & Whitney Canada Corp. Fabricated itd-strut and vane ring for gas turbine engine
US20100132374A1 (en) 2008-11-29 2010-06-03 John Alan Manteiga Turbine frame assembly and method for a gas turbine engine
US20100132371A1 (en) 2008-11-28 2010-06-03 Pratt & Whitney Canada Corp. Mid turbine frame system for gas turbine engine
US7735833B2 (en) 2006-11-14 2010-06-15 The University Of Akron Double padded finger seal
US20100202872A1 (en) 2007-09-07 2010-08-12 Mtu Aero Engines Gmbh Multilayer shielding ring for a flight driving mechanism
US7798768B2 (en) 2006-10-25 2010-09-21 Siemens Energy, Inc. Turbine vane ID support
US20100236244A1 (en) 2006-06-28 2010-09-23 Longardner Robert L Heat absorbing and reflecting shield for air breathing heat engine
US7815417B2 (en) 2006-09-01 2010-10-19 United Technologies Corporation Guide vane for a gas turbine engine
US7824152B2 (en) 2007-05-09 2010-11-02 Siemens Energy, Inc. Multivane segment mounting arrangement for a gas turbine
US20100275614A1 (en) 2009-04-30 2010-11-04 Pratt & Whitney Canada Corp. Structural reinforcement strut for gas turbine case
US20100275572A1 (en) 2009-04-30 2010-11-04 Pratt & Whitney Canada Corp. Oil line insulation system for mid turbine frame
US20100303608A1 (en) * 2006-09-28 2010-12-02 Mitsubishi Heavy Industries, Ltd. Two-shaft gas turbine
US20100307165A1 (en) 2007-12-21 2010-12-09 United Technologies Corp. Gas Turbine Engine Systems Involving I-Beam Struts
US20110000223A1 (en) 2008-02-25 2011-01-06 Volvo Aero Corporation gas turbine component and a method for producing a gas turbine component
US20110005234A1 (en) 2008-02-27 2011-01-13 Mitsubishi Heavy Industries, Ltd. Connection structure of exhaust chamber, support structure of turbine, and gas turbine
US7891165B2 (en) 2007-06-13 2011-02-22 Snecma Exhaust casing hub comprising stress-distributing ribs
US20110061767A1 (en) 2009-09-14 2011-03-17 United Technologies Corporation Component removal tool and method
US7909573B2 (en) 2006-03-17 2011-03-22 Snecma Casing cover in a jet engine
US20110081237A1 (en) 2009-10-01 2011-04-07 Pratt & Whitney Canada Corp. Sealing for vane segments
US20110081240A1 (en) 2009-10-01 2011-04-07 Pratt & Whitney Canada Corp. Fabricated gas turbine vane ring
US20110081239A1 (en) 2009-10-01 2011-04-07 Pratt & Whitney Canada Corp. Fabricated static vane ring
US20110085895A1 (en) 2009-10-09 2011-04-14 Pratt & Whitney Canada Corp. Oil tube with integrated heat shield
US7955446B2 (en) 2005-08-22 2011-06-07 United Technologies Corporation Welding repair method for full hoop structures
US7959409B2 (en) 2007-03-01 2011-06-14 Honeywell International Inc. Repaired vane assemblies and methods of repairing vane assemblies
US20110214433A1 (en) 2010-03-08 2011-09-08 United Technologies Corporation Strain tolerant bound structure for a gas turbine engine
US20110262277A1 (en) 2008-12-18 2011-10-27 Volvo Aero Corporation Gas turbine composite workpiece to be used in gas turbine engine
US8069648B2 (en) 2008-07-03 2011-12-06 United Technologies Corporation Impingement cooling for turbofan exhaust assembly
US20110302929A1 (en) 2010-06-10 2011-12-15 Alstom Technology Ltd Exhaust gas housing for a gas turbine and method for producing same
US8092161B2 (en) 2008-09-24 2012-01-10 Siemens Energy, Inc. Thermal shield at casing joint
US8091371B2 (en) 2008-11-28 2012-01-10 Pratt & Whitney Canada Corp. Mid turbine frame for gas turbine engine
US8099962B2 (en) * 2008-11-28 2012-01-24 Pratt & Whitney Canada Corp. Mid turbine frame system and radial locator for radially centering a bearing for gas turbine engine
US8152451B2 (en) 2008-11-29 2012-04-10 General Electric Company Split fairing for a gas turbine engine
US8162593B2 (en) 2007-03-20 2012-04-24 Snecma Inter-turbine casing with cooling circuit, and turbofan comprising it
US8172526B2 (en) 2007-12-14 2012-05-08 Snecma Sealing a hub cavity of an exhaust casing in a turbomachine
US20120111023A1 (en) 2009-05-08 2012-05-10 Volvo Aero Corporation Supporting structure for a gas turbine engine
US8177488B2 (en) 2008-11-29 2012-05-15 General Electric Company Integrated service tube and impingement baffle for a gas turbine engine
US20120156020A1 (en) 2010-12-20 2012-06-21 General Electric Company Method of repairing a transition piece of a gas turbine engine
US8221071B2 (en) 2008-09-30 2012-07-17 General Electric Company Integrated guide vane assembly
US20120186254A1 (en) 2011-01-24 2012-07-26 Shoko Ito Damage-repairing method of transition piece and transition piece
US20120204569A1 (en) 2011-02-11 2012-08-16 Schubert Paul C Apparatus and methods for eliminating cracking in a turbine exhaust shield
US8245518B2 (en) 2008-11-28 2012-08-21 Pratt & Whitney Canada Corp. Mid turbine frame system for gas turbine engine
US8245399B2 (en) 2009-01-20 2012-08-21 United Technologies Corporation Replacement of part of engine case with dissimilar material
US8282342B2 (en) 2009-02-16 2012-10-09 Rolls-Royce Plc Vane
WO2012158070A1 (fr) 2011-05-16 2012-11-22 Volvo Aero Corporation Carénage d'une structure de turbine à gaz
US20130011242A1 (en) 2011-07-07 2013-01-10 Alexander Beeck Gas turbine engine with angled and radial supports
US8371127B2 (en) 2009-10-01 2013-02-12 Pratt & Whitney Canada Corp. Cooling air system for mid turbine frame
US8616835B2 (en) * 2008-03-28 2013-12-31 Mitsubishi Heavy Industries, Ltd. Gas turbine
US8863531B2 (en) * 2012-07-02 2014-10-21 United Technologies Corporation Cooling apparatus for a mid-turbine frame
US9316153B2 (en) * 2013-01-22 2016-04-19 Siemens Energy, Inc. Purge and cooling air for an exhaust section of a gas turbine assembly

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010018874A (ja) * 2008-07-14 2010-01-28 Kobe Steel Ltd 合金化溶融亜鉛めっき鋼板と合金化溶融亜鉛めっき鋼板の製造方法
AU2010202829A1 (en) * 2009-07-10 2011-01-27 Boshuizen, Trevor Wayne Mr Boat Latch

Patent Citations (167)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2214108A (en) 1938-11-05 1940-09-10 Gen Motors Corp Manufacture of tubing
US4044555A (en) 1958-09-30 1977-08-30 Hayes International Corporation Rear section of jet power plant installations
US3576328A (en) 1968-03-22 1971-04-27 Robert W Vose High pressure seals
US3802046A (en) 1972-01-27 1974-04-09 Chromalloy American Corp Method of making or reconditioning a turbine-nozzle or the like assembly
US3970319A (en) 1972-11-17 1976-07-20 General Motors Corporation Seal structure
US4114248A (en) 1974-12-23 1978-09-19 United Technologies Corporation Method of making resiliently coated metallic finger seals
US4009569A (en) 1975-07-21 1977-03-01 United Technologies Corporation Diffuser-burner casing for a gas turbine engine
US4079587A (en) * 1975-12-10 1978-03-21 Stal-Laval Turbin Ab Multi-stage turbine with interstage spacer-manifold for coolant flow
US4088422A (en) 1976-10-01 1978-05-09 General Electric Company Flexible interstage turbine spacer
US4190397A (en) * 1977-11-23 1980-02-26 General Electric Company Windage shield
US4369016A (en) 1979-12-21 1983-01-18 United Technologies Corporation Turbine intermediate case
US4321007A (en) 1979-12-21 1982-03-23 United Technologies Corporation Outer case cooling for a turbine intermediate case
US4305697A (en) 1980-03-19 1981-12-15 General Electric Company Method and replacement member for repairing a gas turbine engine vane assembly
US4478551A (en) 1981-12-08 1984-10-23 United Technologies Corporation Turbine exhaust case design
US4678113A (en) 1985-02-20 1987-07-07 Rolls-Royce Plc Brush seals
US4645217A (en) 1985-11-29 1987-02-24 United Technologies Corporation Finger seal assembly
US4756536A (en) 1986-12-06 1988-07-12 Rolls-Royce Plc Brush seal
US4793770A (en) 1987-08-06 1988-12-27 General Electric Company Gas turbine engine frame assembly
US4738453A (en) 1987-08-17 1988-04-19 Ide Russell D Hydrodynamic face seal with lift pads
US4920742A (en) 1988-05-31 1990-05-01 General Electric Company Heat shield for gas turbine engine frame
US4987736A (en) 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
US4989406A (en) 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
US4993918A (en) 1989-05-19 1991-02-19 United Technologies Corporation Replaceable fairing for a turbine exhaust case
US4979872A (en) * 1989-06-22 1990-12-25 United Technologies Corporation Bearing compartment support
US5031922A (en) 1989-12-21 1991-07-16 Allied-Signal Inc. Bidirectional finger seal
US5042823A (en) 1989-12-21 1991-08-27 Allied-Signal Inc. Laminated finger seal
US5071138A (en) 1989-12-21 1991-12-10 Allied-Signal Inc. Laminated finger seal
US5076049A (en) 1990-04-02 1991-12-31 General Electric Company Pretensioned frame
US5100158A (en) 1990-08-16 1992-03-31 Eg&G Sealol, Inc. Compliant finer seal
US5474305A (en) 1990-09-18 1995-12-12 Cross Manufacturing Company (1938) Limited Sealing device
US5115642A (en) * 1991-01-07 1992-05-26 United Technologies Corporation Gas turbine engine case with intergral shroud support ribs
US5108116A (en) 1991-05-31 1992-04-28 Allied-Signal Inc. Laminated finger seal with logarithmic curvature
US5174584A (en) 1991-07-15 1992-12-29 General Electric Company Fluid bearing face seal for gas turbine engines
US5169159A (en) 1991-09-30 1992-12-08 General Electric Company Effective sealing device for engine flowpath
US5236302A (en) 1991-10-30 1993-08-17 General Electric Company Turbine disk interstage seal system
US5246295A (en) 1991-10-30 1993-09-21 Ide Russell D Non-contacting mechanical face seal of the gap-type
US5385409A (en) 1991-10-30 1995-01-31 Ide; Russell D. Non-contacting mechanical face seal of the gap-type
US5188507A (en) 1991-11-27 1993-02-23 General Electric Company Low-pressure turbine shroud
US5312227A (en) 1991-12-18 1994-05-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbine casing delimiting an annular gas flow stream divided by radial arms
US5211541A (en) 1991-12-23 1993-05-18 General Electric Company Turbine support assembly including turbine heat shield and bolt retainer assembly
US5269057A (en) 1991-12-24 1993-12-14 Freedom Forge Corporation Method of making replacement airfoil components
US5265807A (en) 1992-06-01 1993-11-30 Rohr, Inc. Aerodynamic stiffening ring for an aircraft turbine engine mixer
US5357744A (en) 1992-06-09 1994-10-25 General Electric Company Segmented turbine flowpath assembly
US5292227A (en) 1992-12-10 1994-03-08 General Electric Company Turbine frame
US5272869A (en) 1992-12-10 1993-12-28 General Electric Company Turbine frame
US5273397A (en) 1993-01-13 1993-12-28 General Electric Company Turbine casing and radiation shield
US5338154A (en) 1993-03-17 1994-08-16 General Electric Company Turbine disk interstage seal axial retaining ring
US5401036A (en) 1993-03-22 1995-03-28 Eg & G Sealol, Inc. Brush seal device having a recessed back plate
US5483792A (en) 1993-05-05 1996-01-16 General Electric Company Turbine frame stiffening rails
US5370402A (en) 1993-05-07 1994-12-06 Eg&G Sealol, Inc. Pressure balanced compliant seal device
US5691279A (en) 1993-06-22 1997-11-25 The United States Of America As Represented By The Secretary Of The Army C-axis oriented high temperature superconductors deposited onto new compositions of garnet
US5438756A (en) 1993-12-17 1995-08-08 General Electric Company Method for assembling a turbine frame assembly
US5558341A (en) 1995-01-11 1996-09-24 Stein Seal Company Seal for sealing an incompressible fluid between a relatively stationary seal and a movable member
US5632493A (en) 1995-05-04 1997-05-27 Eg&G Sealol, Inc. Compliant pressure balanced seal apparatus
US5851105A (en) 1995-06-28 1998-12-22 General Electric Company Tapered strut frame
US5911400A (en) 1995-09-27 1999-06-15 Hydraulik-Ring Antriebs-Und Steuerungstechnik Gmbh Solenoid valve and method for its manufacture
US5609467A (en) 1995-09-28 1997-03-11 Cooper Cameron Corporation Floating interturbine duct assembly for high temperature power turbine
US5597286A (en) 1995-12-21 1997-01-28 General Electric Company Turbine frame static seal
US5605438A (en) 1995-12-29 1997-02-25 General Electric Co. Casing distortion control for rotating machinery
US5634767A (en) 1996-03-29 1997-06-03 General Electric Company Turbine frame having spindle mounted liner
US5755445A (en) 1996-08-23 1998-05-26 Alliedsignal Inc. Noncontacting finger seal with hydrodynamic foot portion
US6337751B1 (en) 1997-08-26 2002-01-08 Canon Kabushiki Kaisha Sheet feeding apparatus and image processing apparatus
US6163959A (en) 1998-04-09 2000-12-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Method of reducing the gap between a liner and a turbine distributor of a turbojet engine
US6227800B1 (en) 1998-11-24 2001-05-08 General Electric Company Bay cooled turbine casing
US6179560B1 (en) 1998-12-16 2001-01-30 United Technologies Corporation Turbomachinery module with improved maintainability
US6364316B1 (en) 1999-02-11 2002-04-02 Honeywell International Inc. Dual pressure balanced noncontacting finger seal
US6196550B1 (en) 1999-02-11 2001-03-06 Alliedsignal Inc. Pressure balanced finger seal
US6343912B1 (en) 1999-12-07 2002-02-05 General Electric Company Gas turbine or jet engine stator vane frame
US6358001B1 (en) 2000-04-29 2002-03-19 General Electric Company Turbine frame assembly
US6439841B1 (en) 2000-04-29 2002-08-27 General Electric Company Turbine frame assembly
US6578363B2 (en) 2001-03-05 2003-06-17 Mitsubishi Heavy Industries, Ltd. Air-cooled gas turbine exhaust casing
US6511284B2 (en) 2001-06-01 2003-01-28 General Electric Company Methods and apparatus for minimizing gas turbine engine thermal stress
US6601853B2 (en) 2001-06-29 2003-08-05 Eagle Industry Co., Ltd. Brush seal device
US20030025274A1 (en) 2001-08-02 2003-02-06 Honeywell International, Inc. Laminated finger seal with stress reduction
US20030042682A1 (en) 2001-08-29 2003-03-06 Eagle Industry Co., Ltd. Brush seal device
WO2003020469A1 (fr) 2001-08-29 2003-03-13 Volvo Aero Corporation Procede de fabrication d'element de stator ou de rotor
US20030062684A1 (en) 2001-09-28 2003-04-03 Eagle Industry Co., Ltd. Brush seal
US20030062685A1 (en) 2001-09-28 2003-04-03 Eagle Industry Co., Ltd Brush seal and brush seal device
US6805356B2 (en) 2001-09-28 2004-10-19 Eagle Industry Co., Ltd. Brush seal and brush seal device
US6612807B2 (en) 2001-11-15 2003-09-02 General Electric Company Frame hub heating system
US6672833B2 (en) 2001-12-18 2004-01-06 General Electric Company Gas turbine engine frame flowpath liner support
US6736401B2 (en) 2001-12-19 2004-05-18 Honeywell International, Inc. Laminated finger seal with ceramic composition
US6796765B2 (en) 2001-12-27 2004-09-28 General Electric Company Methods and apparatus for assembling gas turbine engine struts
US7055305B2 (en) 2002-02-09 2006-06-06 Alstom Technology Ltd Exhaust gas housing of a thermal engine
US6719524B2 (en) 2002-02-25 2004-04-13 Honeywell International Inc. Method of forming a thermally isolated gas turbine engine housing
US6638013B2 (en) 2002-02-25 2003-10-28 Honeywell International Inc. Thermally isolated housing in gas turbine engine
US6652229B2 (en) 2002-02-27 2003-11-25 General Electric Company Leaf seal support for inner band of a turbine nozzle in a gas turbine engine
US6619030B1 (en) 2002-03-01 2003-09-16 General Electric Company Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors
US20050046113A1 (en) 2002-05-23 2005-03-03 Eagle Industry Co., Ltd. Sheet brush seal
US6935631B2 (en) 2002-05-23 2005-08-30 Eagle Industry Co., Ltd. Sheet brush seal
US7614150B2 (en) 2002-08-14 2009-11-10 Volvo Aero Corporation Method for manufacturing a stator or rotor component
US7200933B2 (en) 2002-08-14 2007-04-10 Volvo Aero Corporation Method for manufacturing a stator component
US6792758B2 (en) 2002-11-07 2004-09-21 Siemens Westinghouse Power Corporation Variable exhaust struts shields
US6811154B2 (en) 2003-02-08 2004-11-02 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Noncontacting finger seal
US7389583B2 (en) 2003-03-21 2008-06-24 Volvo Aero Corporation Method of manufacturing a stator component
US6983608B2 (en) 2003-12-22 2006-01-10 General Electric Company Methods and apparatus for assembling gas turbine engines
US6969826B2 (en) 2004-04-08 2005-11-29 General Electric Company Welding process
US7094026B2 (en) 2004-04-29 2006-08-22 General Electric Company System for sealing an inner retainer segment and support ring in a gas turbine and methods therefor
US7238008B2 (en) 2004-05-28 2007-07-03 General Electric Company Turbine blade retainer seal
US7100358B2 (en) 2004-07-16 2006-09-05 Pratt & Whitney Canada Corp. Turbine exhaust case and method of making
WO2006007686A1 (fr) 2004-07-16 2006-01-26 Pratt & Whitney Canada Corp. Carter d'echappement de turbine et son procede de fabrication
US20060010852A1 (en) 2004-07-16 2006-01-19 Pratt & Whitney Canada Corp. Turbine exhaust case and method of making
US7229249B2 (en) 2004-08-27 2007-06-12 Pratt & Whitney Canada Corp. Lightweight annular interturbine duct
US7249463B2 (en) * 2004-09-15 2007-07-31 General Electric Company Aerodynamic fastener shield for turbomachine
US7367567B2 (en) 2005-03-02 2008-05-06 United Technologies Corporation Low leakage finger seal
US7988799B2 (en) 2005-08-22 2011-08-02 United Technologies Corporation Welding repair method for full hoop structures
US7955446B2 (en) 2005-08-22 2011-06-07 United Technologies Corporation Welding repair method for full hoop structures
US7673461B2 (en) 2005-09-29 2010-03-09 Snecma Structural turbine engine casing
US7371044B2 (en) 2005-10-06 2008-05-13 Siemens Power Generation, Inc. Seal plate for turbine rotor assembly between turbine blade and turbine vane
US7909573B2 (en) 2006-03-17 2011-03-22 Snecma Casing cover in a jet engine
US7677047B2 (en) 2006-03-29 2010-03-16 United Technologies Corporation Inverted stiffened shell panel torque transmission for loaded struts and mid-turbine frames
US7631879B2 (en) 2006-06-21 2009-12-15 General Electric Company “L” butt gap seal between segments in seal assemblies
US20100236244A1 (en) 2006-06-28 2010-09-23 Longardner Robert L Heat absorbing and reflecting shield for air breathing heat engine
US7815417B2 (en) 2006-09-01 2010-10-19 United Technologies Corporation Guide vane for a gas turbine engine
US20100303608A1 (en) * 2006-09-28 2010-12-02 Mitsubishi Heavy Industries, Ltd. Two-shaft gas turbine
US7798768B2 (en) 2006-10-25 2010-09-21 Siemens Energy, Inc. Turbine vane ID support
US7735833B2 (en) 2006-11-14 2010-06-15 The University Of Akron Double padded finger seal
US7959409B2 (en) 2007-03-01 2011-06-14 Honeywell International Inc. Repaired vane assemblies and methods of repairing vane assemblies
US20080216300A1 (en) 2007-03-06 2008-09-11 United Technologies Corporation Splitter fairing repair
US8162593B2 (en) 2007-03-20 2012-04-24 Snecma Inter-turbine casing with cooling circuit, and turbofan comprising it
US7824152B2 (en) 2007-05-09 2010-11-02 Siemens Energy, Inc. Multivane segment mounting arrangement for a gas turbine
US7891165B2 (en) 2007-06-13 2011-02-22 Snecma Exhaust casing hub comprising stress-distributing ribs
US20090053046A1 (en) * 2007-08-23 2009-02-26 General Electric Company Method, system and apparatus for turbine diffuser sealing
US20100202872A1 (en) 2007-09-07 2010-08-12 Mtu Aero Engines Gmbh Multilayer shielding ring for a flight driving mechanism
US20090155069A1 (en) 2007-12-12 2009-06-18 Eric Durocher Axial loading element for turbine vane
US8172526B2 (en) 2007-12-14 2012-05-08 Snecma Sealing a hub cavity of an exhaust casing in a turbomachine
US20100307165A1 (en) 2007-12-21 2010-12-09 United Technologies Corp. Gas Turbine Engine Systems Involving I-Beam Struts
US20110000223A1 (en) 2008-02-25 2011-01-06 Volvo Aero Corporation gas turbine component and a method for producing a gas turbine component
US20110005234A1 (en) 2008-02-27 2011-01-13 Mitsubishi Heavy Industries, Ltd. Connection structure of exhaust chamber, support structure of turbine, and gas turbine
US8616835B2 (en) * 2008-03-28 2013-12-31 Mitsubishi Heavy Industries, Ltd. Gas turbine
WO2009157817A1 (fr) 2008-06-26 2009-12-30 Volvo Aero Corporation Ensemble aube, procédé de fabrication associé, et turbomachine équipée de cet ensemble aube
US8069648B2 (en) 2008-07-03 2011-12-06 United Technologies Corporation Impingement cooling for turbofan exhaust assembly
WO2010002295A1 (fr) 2008-07-04 2010-01-07 Volvo Aero Corporation Procédé de soudage
US8083465B2 (en) 2008-09-05 2011-12-27 United Technologies Corporation Repaired turbine exhaust strut heat shield vanes and repair methods
US20100061846A1 (en) 2008-09-05 2010-03-11 United Technologies Corporation Repaired turbine exhaust strut heat shield vanes and repair methods
US8092161B2 (en) 2008-09-24 2012-01-10 Siemens Energy, Inc. Thermal shield at casing joint
US8221071B2 (en) 2008-09-30 2012-07-17 General Electric Company Integrated guide vane assembly
US8091371B2 (en) 2008-11-28 2012-01-10 Pratt & Whitney Canada Corp. Mid turbine frame for gas turbine engine
US20100132377A1 (en) 2008-11-28 2010-06-03 Pratt & Whitney Canada Corp. Fabricated itd-strut and vane ring for gas turbine engine
US8245518B2 (en) 2008-11-28 2012-08-21 Pratt & Whitney Canada Corp. Mid turbine frame system for gas turbine engine
US20100132371A1 (en) 2008-11-28 2010-06-03 Pratt & Whitney Canada Corp. Mid turbine frame system for gas turbine engine
US8099962B2 (en) * 2008-11-28 2012-01-24 Pratt & Whitney Canada Corp. Mid turbine frame system and radial locator for radially centering a bearing for gas turbine engine
US20100132374A1 (en) 2008-11-29 2010-06-03 John Alan Manteiga Turbine frame assembly and method for a gas turbine engine
US8177488B2 (en) 2008-11-29 2012-05-15 General Electric Company Integrated service tube and impingement baffle for a gas turbine engine
US8371812B2 (en) 2008-11-29 2013-02-12 General Electric Company Turbine frame assembly and method for a gas turbine engine
US8152451B2 (en) 2008-11-29 2012-04-10 General Electric Company Split fairing for a gas turbine engine
US20110262277A1 (en) 2008-12-18 2011-10-27 Volvo Aero Corporation Gas turbine composite workpiece to be used in gas turbine engine
US8245399B2 (en) 2009-01-20 2012-08-21 United Technologies Corporation Replacement of part of engine case with dissimilar material
US8282342B2 (en) 2009-02-16 2012-10-09 Rolls-Royce Plc Vane
US20100275572A1 (en) 2009-04-30 2010-11-04 Pratt & Whitney Canada Corp. Oil line insulation system for mid turbine frame
US20100275614A1 (en) 2009-04-30 2010-11-04 Pratt & Whitney Canada Corp. Structural reinforcement strut for gas turbine case
US20120111023A1 (en) 2009-05-08 2012-05-10 Volvo Aero Corporation Supporting structure for a gas turbine engine
US20110061767A1 (en) 2009-09-14 2011-03-17 United Technologies Corporation Component removal tool and method
US8371127B2 (en) 2009-10-01 2013-02-12 Pratt & Whitney Canada Corp. Cooling air system for mid turbine frame
US20110081237A1 (en) 2009-10-01 2011-04-07 Pratt & Whitney Canada Corp. Sealing for vane segments
US20110081239A1 (en) 2009-10-01 2011-04-07 Pratt & Whitney Canada Corp. Fabricated static vane ring
US20110081240A1 (en) 2009-10-01 2011-04-07 Pratt & Whitney Canada Corp. Fabricated gas turbine vane ring
US20110085895A1 (en) 2009-10-09 2011-04-14 Pratt & Whitney Canada Corp. Oil tube with integrated heat shield
US20110214433A1 (en) 2010-03-08 2011-09-08 United Technologies Corporation Strain tolerant bound structure for a gas turbine engine
US20110302929A1 (en) 2010-06-10 2011-12-15 Alstom Technology Ltd Exhaust gas housing for a gas turbine and method for producing same
US20120156020A1 (en) 2010-12-20 2012-06-21 General Electric Company Method of repairing a transition piece of a gas turbine engine
US20120186254A1 (en) 2011-01-24 2012-07-26 Shoko Ito Damage-repairing method of transition piece and transition piece
US20120204569A1 (en) 2011-02-11 2012-08-16 Schubert Paul C Apparatus and methods for eliminating cracking in a turbine exhaust shield
WO2012158070A1 (fr) 2011-05-16 2012-11-22 Volvo Aero Corporation Carénage d'une structure de turbine à gaz
US20130011242A1 (en) 2011-07-07 2013-01-10 Alexander Beeck Gas turbine engine with angled and radial supports
US8863531B2 (en) * 2012-07-02 2014-10-21 United Technologies Corporation Cooling apparatus for a mid-turbine frame
US9316153B2 (en) * 2013-01-22 2016-04-19 Siemens Energy, Inc. Purge and cooling air for an exhaust section of a gas turbine assembly

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
HPAlloys, High Temperature Alloys, accessed Feb. 28, 2018, https://www.hpalloy.com/Alloys/hightemperature.aspx, Hastelloy and Inconel. *
International Search Report and Written Opinion from PCT Application Serial No. PCT/US2013/076394, dated Apr. 14, 2014, 13 pages.
TEADIT, Metallic Materials, accessed Feb. 28, 2018, http://www.allsealsinc.com/teadit/TypicalMetalProperties.pdf, Stainless steels. *

Also Published As

Publication number Publication date
US20150337683A1 (en) 2015-11-26
WO2014105604A1 (fr) 2014-07-03

Similar Documents

Publication Publication Date Title
US9879556B2 (en) Cooled finger seal
US10006306B2 (en) Turbine exhaust case architecture
US9115596B2 (en) Blade outer air seal having anti-rotation feature
US20150337687A1 (en) Split cast vane fairing
EP2875223B1 (fr) Joint à air d'extérieur d'aube avec extension pointant vers l'intérieur
EP2938837B1 (fr) Ensemble de joint d'étanchéité de turbine à gaz et support de joint d'étanchéité
US20150337682A1 (en) Cooling architecture for turbine exhaust case
US9890663B2 (en) Turbine exhaust case multi-piece frame
EP3066318B1 (fr) Boîtier diffuseur interne destiné à un moteur à turbine à gaz
US9976442B2 (en) Heat shield based air dam for a turbine exhaust case
US11067276B2 (en) Igniter seal arrangement for a combustion chamber
EP2938857B1 (fr) Bouclier thermique pour le refroidissement d'une entretoise
US10428823B2 (en) Centrifugal compressor apparatus
US10329957B2 (en) Turbine exhaust case multi-piece framed
US10240481B2 (en) Angled cut to direct radiative heat load
US10472987B2 (en) Heat shield for a casing
US20240410581A1 (en) Combustor assembly for a gas turbine engine

Legal Events

Date Code Title Description
AS Assignment

Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SCOTT, JONATHAN ARIEL;CHUONG, CONWAY;REEL/FRAME:035924/0469

Effective date: 20140122

STCF Information on status: patent grant

Free format text: PATENTED CASE

AS Assignment

Owner name: RAYTHEON TECHNOLOGIES CORPORATION, MASSACHUSETTS

Free format text: CHANGE OF NAME;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:054062/0001

Effective date: 20200403

AS Assignment

Owner name: RAYTHEON TECHNOLOGIES CORPORATION, CONNECTICUT

Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:055659/0001

Effective date: 20200403

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 4

AS Assignment

Owner name: RTX CORPORATION, CONNECTICUT

Free format text: CHANGE OF NAME;ASSIGNOR:RAYTHEON TECHNOLOGIES CORPORATION;REEL/FRAME:064714/0001

Effective date: 20230714